EP3189215A1 - A transition-to-turbine seal assembly - Google Patents

A transition-to-turbine seal assembly

Info

Publication number
EP3189215A1
EP3189215A1 EP14767246.3A EP14767246A EP3189215A1 EP 3189215 A1 EP3189215 A1 EP 3189215A1 EP 14767246 A EP14767246 A EP 14767246A EP 3189215 A1 EP3189215 A1 EP 3189215A1
Authority
EP
European Patent Office
Prior art keywords
transition
turbine
seal member
seal
piece
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14767246.3A
Other languages
German (de)
French (fr)
Other versions
EP3189215B1 (en
Inventor
Robert H. Bartley
Matthias Hase
Adam J. Weaver
Lashanda N. WILLIAMS
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3189215A1 publication Critical patent/EP3189215A1/en
Application granted granted Critical
Publication of EP3189215B1 publication Critical patent/EP3189215B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • Disclosed embodiments are generally related to a combustion turbine engine, and, more particularly, to a seal assembly between a transition and a turbine of such engine, referred to herein as a transition-to-turbine seal assembly.
  • a number of combustion chambers combust fuel mixed with compressed air, and a hot working gas flowing from these combustion chambers is passed via respective transitions (also referred to by some in the art as ducts and tail tubes) to respective entrances of the turbine.
  • transitions also referred to by some in the art as ducts and tail tubes
  • a plurality of combustion chambers may be arranged radially about a longitudinal axis of the turbine engine, and likewise radially arranged transitions comprise outlet ends that converge to form an annular inflow of working gas to the turbine entrance.
  • Each transition exit is joined by a number of seals each of which bridges a gap between a portion of the exit and one or more turbine components.
  • FIG. 1 is a simplified schematic of one non-limiting embodiment of a combustion turbine engine that can benefit from aspects of the present invention.
  • FIG. 2 is a schematic illustrating one non-limiting embodiment of a transition-to- turbine seal assembly embodying aspects of the present invention.
  • FIG. 3 is a schematic illustrating another non-limiting embodiment of a transition- to-turbine seal assembly embodying aspects of the present invention.
  • FIG. 4 is an exploded view of articulating pieces in one non-limiting embodiment of an outer diameter seal member.
  • FIG. 5 is a hidden-line view of an assembly of the articulating pieces shown in
  • FIG. 6 is an exploded view of articulating pieces in one non-limiting embodiment of an inner diameter seal member.
  • FIG. 7 is a hidden-line view of an assembly of the articulating pieces shown in
  • FIG. 8 is an isometric view of a plurality of a transition-to-turbine seal assemblies embodying aspects of the present invention as may be annularly interconnected to an annular array of transitions to seal an outer diameter and inner diameter of a transition- to-turbine interface.
  • the present inventors have recognized certain issues arising in connection with certain known transition-to-turbine seal structures that involve seal affixing with anchoring tabs arranged on neighboring transitions, and where differing motion that can arise between such neighboring transitions can result in relatively high levels of mechanical stress to the seal structures, which can lead to excessive wear and to the formation of cracks in such seal structures, and, consequently, to a shortened seal life.
  • the present inventors propose an innovative transition-to- turbine seal assembly, where differing motion between neighboring transitions is practically decoupled, and thus, in a cost-effective manner, the proposed transition-to- turbine seal assembly is expected to result in relatively lower levels of stress to seal members, with a concomitant reduction in seal wear and cracking, which is conducive to a more reliable and longer-lasting transition-to-turbine seal assembly.
  • FIG. 1 is a simplified schematic of one non-limiting embodiment of a combustion turbine engine 10, such as gas turbine engine, that can benefit from aspects of the present invention.
  • Combustion turbine engine 10 comprises a compressor 12, a combustor 14, a combustion chamber 16 (such as a can-annular type), and a turbine 18.
  • compressor 12 takes in ambient air and provides compressed air to a diffuser 20, which passes the compressed air to a plenum 22 through which the compressed air passes to combustor 14, which mixes the compressed air with fuel, and provides combusted, hot working gas via a transition 24 to turbine 18, which can drive power-generating equipment (not shown) to generate electricity.
  • a shaft 26 is shown connecting turbine 18 to drive compressor 12.
  • a transition-to-turbine seal assembly 50 embodying aspects of the present invention is disposed at a junction between transition 24 and turbine 18, and is described in greater detail below.
  • a transition-to- turbine seal assembly 50 comprises a first seal member 52, such as an outer diameter seal member, comprising one or more anchoring tabs 54 affixed only to an associated transition, such as a corresponding outer diameter section of an associated transition 56.
  • Transition-to-turbine seal assembly 50 further comprises a second seal member 58, such as inner diameter seal member, comprising one or more anchoring tabs 60 affixed only to associated transition 56, such as an inner diameter section of an associated transition 56.
  • seal members 52, 58 do not involve anchoring tabs arranged on two or more neighboring transitions, such as neighboring transitions 56 and 57.
  • seal structures that involve affixing with anchoring tabs arranged on neighboring transitions differing motion that can arise between such neighboring transitions can result in relatively high levels of mechanical stress to the seal structures, which can lead to excessive wear and to the formation of cracks in such jointly anchored structures, and, consequently, to a shortened seal life.
  • seal members 52, 58 are not affixed to neighboring transitions, such as neighboring transition 57, but, for example, only to the associated transition 56, any differing motion between neighboring transitions 56 and 57 is practically no longer a factor and this is expected to result in relatively lower levels of stress to seal members 52, 58, and a concomitant reduction in seal wear and cracking, which is conducive to a relatively longer-lasting and more reliable transition-to-turbine seal assembly 50.
  • outer diameter seal member 52 and inner diameter seal member 58 are positioned to respectively extend between mutually opposed sides 62 of associated transition 56.
  • respective ends of seal member 52 and second seal member 58 may comprise a shiplap (e.g., overlapping) joint 66 positioned at a gap 68 between neighboring transitions 56, 57 effective for annularly interconnecting the respective seal members associated with such neighboring transitions. That is, effective for annularly interconnecting outer diameter seam member 52 in transition 56 to an adjacent outer diameter seam member 52 in transition 57; or, similarly, effective for annularly interconnecting inner diameter seam member 58 in transition 56 to an adjacent inner diameter seam member 58 in transition 57.
  • shiplap e.g., overlapping
  • outer diameter seal member 52 and inner diameter seal member 58 --respectively affixed only to transition 56 by way of anchoring tabs 54 and 60- may further comprise respective seal member portions, schematically represented by line 64, that span a corresponding portion of neighboring transition 57, where seal member portion 64 is free from anchoring with respect to neighboring transition 57.
  • a respective shiplap joint 70 at the end of seal member portions 64 may be used for annularly interconnecting the seals associated with such neighboring transitions.
  • FIG. 4 is an exploded view of articulating pieces of a first seal member 100, such as an outer diameter seal member, comprising an outer piece 102 to be superimposed on an inner piece 104, as may be appreciated in the hidden line view shown in FIG. 5.
  • Outer piece 102 and inner piece 104 each comprises a respective plurality of articulating segments 108, 106 disposed between respective pluralities of flexible joints 1 12, 1 10, such as slits, arranged to provide a degree of freedom to first seal member 100 along a first axis 1 14 (FIG. 5) that in one non-limiting embodiment extends along a circumferential direction.
  • the respective pluralities of flexible joints 1 12, 1 10 in outer piece 102 and inner piece 104 each comprises a respective plurality of slits arranged in a non-coinciding pattern with respect to one another when outer piece 102 is superimposed on inner piece 104, as may be appreciated in FIG. 5.
  • the non- coinciding arrangement between the respective slits in outer piece 102 and inner piece 104 is effective to improve the sealing functionality while providing enhanced flexibility conducive to relatively lower levels of stress to the seal members.
  • the number and spacing between the slits may be tailored based on the needs of a given application, such as involving the structural and/or sealing performance of the seal members.
  • the slit arrangements illustrated in the figures should be construed in an example sense and not in a limiting sense. It will be further appreciated that the articulating pieces may be manufactured in a practically straight shape, and then, during an installation stage, the articulating pieces could be manipulated to a desired shape, as may include imparting a desired degree of curvature to a plurality of seal members made up of such articulating pieces to form in combination an annular seal .
  • FIG. 6 is an exploded view of articulating pieces in a second seal member 120, such as an inner diameter seal member, comprising an outer piece 122 to be
  • Outer piece 122 and inner piece 124 each comprises a respective plurality of articulating segments 126, 128 disposed between respective pluralities of flexible joints 130, 132, such as slits, arranged to provide a degree of freedom to second seal member 120 along a second axis 134 that in one non-limiting embodiment extends along an axial direction.
  • the respective pluralities of flexible joints 130, 132 in outer piece 122 and inner piece 124 each comprises a respective plurality of slits arranged in a non-coinciding pattern with respect to one another when outer piece 122 is superimposed on inner piece 124, as may be appreciated in FIG. 7.
  • FIG. 8 is an isometric view of one non-limiting embodiment of a plurality of transition-to-turbine seal assemblies comprising outer diameter seal members 202 and inner diameter seal members 204 embodying aspects of the present invention, as may be annularly interconnected to an annular array of transitions 200 to seal an outer diameter and inner diameter of a transition-to-turbine interface.
  • seal members 202 and 204 may comprise: members affixed only to an associated transition (not affixed to neighboring transitions), as disclosed in the context of FIGs 2-3; articulating pieces as disclosed in the context of FIGs. 4-7; or combinations of such members.
  • the enhanced seal flexibility achieved with the articulating pieces can provide an effective and thorough sealing functionality, even at seal locations not expected to do so, such as the shiplap joints positioned at the gaps between neighboring transitions.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Abstract

A transition-to-turbine seal assembly is provided. Seal members (52, 58) may include one or more anchoring tabs (54, 60) affixed only to an associated transition (56) and not to a neighboring transition (57). Thus, seal members (52, 58) may be practically free from high stress levels due to differing motion that can arise between neighboring transitions (56, 57). Additionally, seal members (100, 120) may include articulating segments (106, 108, 126, 128) arranged to provide a respective degree of freedom along a desired direction.

Description

A TRANSITION-TO-TURBINE SEAL ASSEMBLY
FIELD OF THE INVENTION
Disclosed embodiments are generally related to a combustion turbine engine, and, more particularly, to a seal assembly between a transition and a turbine of such engine, referred to herein as a transition-to-turbine seal assembly.
BACKGROUND OF THE INVENTION
In a combustion turbine engine, such as a gas turbine engine, a number of combustion chambers combust fuel mixed with compressed air, and a hot working gas flowing from these combustion chambers is passed via respective transitions (also referred to by some in the art as ducts and tail tubes) to respective entrances of the turbine. More specifically, a plurality of combustion chambers may be arranged radially about a longitudinal axis of the turbine engine, and likewise radially arranged transitions comprise outlet ends that converge to form an annular inflow of working gas to the turbine entrance. Each transition exit is joined by a number of seals each of which bridges a gap between a portion of the exit and one or more turbine components. A number of factors -such as adjacent component growth, variances due to thermal expansion, mechanical loads, vibrational forces from combustion dynamics, etc.-- can present challenges regarding durability and performance of such seals.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention is explained in the following description in view of the drawings that show:
FIG. 1 is a simplified schematic of one non-limiting embodiment of a combustion turbine engine that can benefit from aspects of the present invention.
FIG. 2 is a schematic illustrating one non-limiting embodiment of a transition-to- turbine seal assembly embodying aspects of the present invention.
FIG. 3 is a schematic illustrating another non-limiting embodiment of a transition- to-turbine seal assembly embodying aspects of the present invention. FIG. 4 is an exploded view of articulating pieces in one non-limiting embodiment of an outer diameter seal member.
FIG. 5 is a hidden-line view of an assembly of the articulating pieces shown in
FIG. 4.
FIG. 6 is an exploded view of articulating pieces in one non-limiting embodiment of an inner diameter seal member.
FIG. 7 is a hidden-line view of an assembly of the articulating pieces shown in
FIG. 6.
FIG. 8 is an isometric view of a plurality of a transition-to-turbine seal assemblies embodying aspects of the present invention as may be annularly interconnected to an annular array of transitions to seal an outer diameter and inner diameter of a transition- to-turbine interface.
DETAILED DESCRIPTION OF THE INVENTION
The present inventors have recognized certain issues arising in connection with certain known transition-to-turbine seal structures that involve seal affixing with anchoring tabs arranged on neighboring transitions, and where differing motion that can arise between such neighboring transitions can result in relatively high levels of mechanical stress to the seal structures, which can lead to excessive wear and to the formation of cracks in such seal structures, and, consequently, to a shortened seal life. In view of such recognition, the present inventors propose an innovative transition-to- turbine seal assembly, where differing motion between neighboring transitions is practically decoupled, and thus, in a cost-effective manner, the proposed transition-to- turbine seal assembly is expected to result in relatively lower levels of stress to seal members, with a concomitant reduction in seal wear and cracking, which is conducive to a more reliable and longer-lasting transition-to-turbine seal assembly.
FIG. 1 is a simplified schematic of one non-limiting embodiment of a combustion turbine engine 10, such as gas turbine engine, that can benefit from aspects of the present invention. Combustion turbine engine 10 comprises a compressor 12, a combustor 14, a combustion chamber 16 (such as a can-annular type), and a turbine 18. During operation, compressor 12 takes in ambient air and provides compressed air to a diffuser 20, which passes the compressed air to a plenum 22 through which the compressed air passes to combustor 14, which mixes the compressed air with fuel, and provides combusted, hot working gas via a transition 24 to turbine 18, which can drive power-generating equipment (not shown) to generate electricity. A shaft 26 is shown connecting turbine 18 to drive compressor 12. A transition-to-turbine seal assembly 50 embodying aspects of the present invention is disposed at a junction between transition 24 and turbine 18, and is described in greater detail below.
In one non-limiting embodiment, as may be appreciated in FIG. 2, a transition-to- turbine seal assembly 50 comprises a first seal member 52, such as an outer diameter seal member, comprising one or more anchoring tabs 54 affixed only to an associated transition, such as a corresponding outer diameter section of an associated transition 56. Transition-to-turbine seal assembly 50 further comprises a second seal member 58, such as inner diameter seal member, comprising one or more anchoring tabs 60 affixed only to associated transition 56, such as an inner diameter section of an associated transition 56.
That is, opposite to certain prior art seal structures that involve affixing by way of anchoring tabs arranged on neighboring transitions, seal members 52, 58 do not involve anchoring tabs arranged on two or more neighboring transitions, such as neighboring transitions 56 and 57. In prior art seal structures that involve affixing with anchoring tabs arranged on neighboring transitions, differing motion that can arise between such neighboring transitions can result in relatively high levels of mechanical stress to the seal structures, which can lead to excessive wear and to the formation of cracks in such jointly anchored structures, and, consequently, to a shortened seal life.
Since in this presently disclosed embodiment, seal members 52, 58 are not affixed to neighboring transitions, such as neighboring transition 57, but, for example, only to the associated transition 56, any differing motion between neighboring transitions 56 and 57 is practically no longer a factor and this is expected to result in relatively lower levels of stress to seal members 52, 58, and a concomitant reduction in seal wear and cracking, which is conducive to a relatively longer-lasting and more reliable transition-to-turbine seal assembly 50. In one non-limiting embodiment, as may be appreciated in FIG. 2, outer diameter seal member 52 and inner diameter seal member 58 are positioned to respectively extend between mutually opposed sides 62 of associated transition 56. In this embodiment, respective ends of seal member 52 and second seal member 58 may comprise a shiplap (e.g., overlapping) joint 66 positioned at a gap 68 between neighboring transitions 56, 57 effective for annularly interconnecting the respective seal members associated with such neighboring transitions. That is, effective for annularly interconnecting outer diameter seam member 52 in transition 56 to an adjacent outer diameter seam member 52 in transition 57; or, similarly, effective for annularly interconnecting inner diameter seam member 58 in transition 56 to an adjacent inner diameter seam member 58 in transition 57.
In another non-limiting embodiment, as may be appreciated in FIG. 3, outer diameter seal member 52 and inner diameter seal member 58 --respectively affixed only to transition 56 by way of anchoring tabs 54 and 60- may further comprise respective seal member portions, schematically represented by line 64, that span a corresponding portion of neighboring transition 57, where seal member portion 64 is free from anchoring with respect to neighboring transition 57. A respective shiplap joint 70 at the end of seal member portions 64 may be used for annularly interconnecting the seals associated with such neighboring transitions.
FIG. 4 is an exploded view of articulating pieces of a first seal member 100, such as an outer diameter seal member, comprising an outer piece 102 to be superimposed on an inner piece 104, as may be appreciated in the hidden line view shown in FIG. 5. Outer piece 102 and inner piece 104 each comprises a respective plurality of articulating segments 108, 106 disposed between respective pluralities of flexible joints 1 12, 1 10, such as slits, arranged to provide a degree of freedom to first seal member 100 along a first axis 1 14 (FIG. 5) that in one non-limiting embodiment extends along a circumferential direction.
The respective pluralities of flexible joints 1 12, 1 10 in outer piece 102 and inner piece 104 each comprises a respective plurality of slits arranged in a non-coinciding pattern with respect to one another when outer piece 102 is superimposed on inner piece 104, as may be appreciated in FIG. 5. It will be appreciated that the non- coinciding arrangement between the respective slits in outer piece 102 and inner piece 104 is effective to improve the sealing functionality while providing enhanced flexibility conducive to relatively lower levels of stress to the seal members. It will be appreciated that the number and spacing between the slits may be tailored based on the needs of a given application, such as involving the structural and/or sealing performance of the seal members. Accordingly, the slit arrangements illustrated in the figures should be construed in an example sense and not in a limiting sense. It will be further appreciated that the articulating pieces may be manufactured in a practically straight shape, and then, during an installation stage, the articulating pieces could be manipulated to a desired shape, as may include imparting a desired degree of curvature to a plurality of seal members made up of such articulating pieces to form in combination an annular seal .
FIG. 6 is an exploded view of articulating pieces in a second seal member 120, such as an inner diameter seal member, comprising an outer piece 122 to be
superimposed on an inner piece 124, as may be appreciated in the hidden line view shown in FIG. 7. Outer piece 122 and inner piece 124 each comprises a respective plurality of articulating segments 126, 128 disposed between respective pluralities of flexible joints 130, 132, such as slits, arranged to provide a degree of freedom to second seal member 120 along a second axis 134 that in one non-limiting embodiment extends along an axial direction. The respective pluralities of flexible joints 130, 132 in outer piece 122 and inner piece 124 each comprises a respective plurality of slits arranged in a non-coinciding pattern with respect to one another when outer piece 122 is superimposed on inner piece 124, as may be appreciated in FIG. 7.
FIG. 8 is an isometric view of one non-limiting embodiment of a plurality of transition-to-turbine seal assemblies comprising outer diameter seal members 202 and inner diameter seal members 204 embodying aspects of the present invention, as may be annularly interconnected to an annular array of transitions 200 to seal an outer diameter and inner diameter of a transition-to-turbine interface. It will be appreciated that seal members 202 and 204 may comprise: members affixed only to an associated transition (not affixed to neighboring transitions), as disclosed in the context of FIGs 2-3; articulating pieces as disclosed in the context of FIGs. 4-7; or combinations of such members. For example, it is envisioned that in one non-limiting embodiment the enhanced seal flexibility achieved with the articulating pieces can provide an effective and thorough sealing functionality, even at seal locations not expected to do so, such as the shiplap joints positioned at the gaps between neighboring transitions.
While various embodiments of the present invention have been shown and described herein, it will be apparent that such embodiments are provided by way of example only. Numerous variations, changes and substitutions may be made without departing from the invention herein. Accordingly, it is intended that the invention be limited only by the spirit and scope of the appended claims.

Claims

The invention claimed is: 1 . A transition-to-turbine seal assembly comprising:
a first seal member comprising an outer piece superimposed on an inner piece, wherein the outer piece and the inner piece each comprises a respective plurality of articulating segments disposed between respective pluralities of flexible joints arranged to provide a degree of freedom to the first seal member along a first axis.
2. The transition-to-turbine seal assembly of claim 1 , wherein the respective pluralities of flexible joints in the outer piece and the inner piece each comprises a respective plurality of slits arranged in a non-coinciding pattern with respect to one another when the outer piece is superimposed on the inner piece.
3. The transition-to-turbine seal assembly of claim 2, further comprising a second seal member comprising an outer piece superimposed on an inner piece, wherein the outer piece and the inner piece each comprises a respective plurality of articulating segments disposed between respective pluralities of flexible joints arranged to provide a degree of freedom to the second seal member along a second axis.
4. The transition-to-turbine seal assembly of claim 3, wherein the first seal member comprises an outer diameter seal member and the first axis extends along a circumferential direction, and further wherein the second seal member comprises an inner diameter seal member and the second axis extends along an axial direction.
5. The transition-to-turbine seal assembly of claim 3, wherein the first seal member and the second seal member each comprises at least one anchoring tab affixed only to an associated transition.
6. The transition-to-turbine seal assembly of claim 5, wherein the first seal member and the second seal member are positioned to respectively extend between mutually opposed sides of the associated transition.
7. The transition-to-turbine seal assembly of claim 6, wherein respective ends of the first seal member and the second seal member comprise a shiplap joint positioned at a gap between neighboring transitions.
8. The transition-to-turbine seal assembly of any of claims 3-7 inclusive, comprising a plurality of first seal members annularly interconnected to seal an outer diameter of a transition-to-turbine interface and a plurality of second seal members annularly interconnected to seal an inner diameter of the transition-to-turbine interface.
9. A combustion turbine engine comprising the transition-to-turbine seal assembly of any of claims 1 -7 inclusive.
10. A transition-to-turbine seal assembly comprising:
an outer diameter seal member comprising at least one anchoring tab affixed only to an associated transition.
1 1 . The transition-to-turbine seal assembly of claim 10, further comprising an inner diameter seal member comprising at least one anchoring tab affixed only to the associated transition.
12. The transition-to-turbine seal assembly of claim 1 1 , wherein the outer diameter seal member and the inner diameter seal member are positioned to respectively extend between mutually opposed sides of the associated transition.
13. The transition-to-turbine seal assembly of claim 10, wherein at least one of the outer diameter seal member and the inner diameter seal member comprises a seal member portion that spans a corresponding portion of a neighboring transition, wherein the seal member portion is free from anchoring with respect to the neighboring transition.
14. The transition-to-turbine seal assembly of claim 10, wherein the outer diameter seal comprises an outer piece superimposed on an inner piece, wherein the outer piece and the inner piece each comprises a respective plurality of articulating segments arranged between respective pluralities of flexible joints to provide a degree freedom to the outer diameter seal member along a first axis.
15. The transition-to-turbine seal assembly of claim 14, wherein the respective pluralities of flexible joints in the outer piece and the inner piece each comprises a respective plurality of slits arranged in a non-coinciding pattern with respect to one another when the outer piece is superimposed on the inner piece.
16. The transition-to-turbine seal assembly of claim 15, wherein the inner diameter seal member comprises an outer piece superimposed on an inner piece, wherein the outer piece and the inner piece each comprises a respective plurality of articulating segments arranged between respective pluralities of flexible joints to provide a degree of freedom to the inner diameter seal member along a second axis.
17. The transition-to-turbine seal assembly of claim 16, wherein the first axis extends along a circumferential direction and the second axis extends along an axial direction.
18. The transition-to-turbine seal assembly of claim 16, wherein the outer diameter seal member and the inner diameter seal member are positioned to
respectively extend between mutually opposed sides of the associated transition.
19. The transition-to-turbine seal assembly of claim 18, wherein respective ends of the outer diameter seal member and the inner diameter seal member comprise a shiplap joint positioned intermediate neighboring transitions.
20. A combustion turbine engine comprising the transition-to-turbine seal assembly of any of claims 10-19 inclusive.
21 . An annular seal to seal a transition-to-turbine interface comprising a respective plurality of annularly interconnected inner diameter members and a respective plurality of outer diameter members of the transition-to-turbine seal assemblies of any of claims 1 1 -19 inclusive.
EP14767246.3A 2014-09-05 2014-09-05 A transition-to-turbine seal assembly Active EP3189215B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2014/054264 WO2016036382A1 (en) 2014-09-05 2014-09-05 A transition-to-turbine seal assembly

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EP3189215A1 true EP3189215A1 (en) 2017-07-12
EP3189215B1 EP3189215B1 (en) 2021-04-28

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US (1) US20170284210A1 (en)
EP (1) EP3189215B1 (en)
JP (1) JP6545257B2 (en)
CN (1) CN106605041B (en)
WO (1) WO2016036382A1 (en)

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US20200300105A1 (en) * 2016-03-25 2020-09-24 Siemens Aktiengesellschaft Gas turbine engine, corresponding seal section and integrated exit piece
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US10669939B2 (en) * 2016-10-26 2020-06-02 Raytheon Technologies Corporation Combustor seal for a gas turbine engine combustor
US11248705B2 (en) * 2018-06-19 2022-02-15 General Electric Company Curved seal with relief cuts for adjacent gas turbine components
US11905837B2 (en) * 2022-03-23 2024-02-20 General Electric Company Sealing system including a seal assembly between components

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Also Published As

Publication number Publication date
JP6545257B2 (en) 2019-07-17
JP2017530292A (en) 2017-10-12
EP3189215B1 (en) 2021-04-28
CN106605041B (en) 2018-09-11
CN106605041A (en) 2017-04-26
WO2016036382A1 (en) 2016-03-10
US20170284210A1 (en) 2017-10-05

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